Open breech high rate automatic rocket launcher

ABSTRACT

AN OPEN BREECH, HIGH RATE, AUTOMATIC, ROCKET LAUNCHER PROVIDED WITH A PAIR OF LAUNCHING TUBES AND A FOUR CHAMBER REVOLVING AND RECIPROCATING REVOLVER. THE REVOLUTION OF THE REVOLVER ALLOWS TWO CHAMBERS TO BE ALIGNED WITH THE LAUNCHING TUBES WHILE THE OTHER TWO CHAMBERS ARE BEING LOADED. THE RECIPROCATING MOTION OF THE REVOLVER ALLOWS IT TO MOVE FOREWARD TO SEAL AND ALIGN THE FIRING CHAMBERS WITH THE LAUNCHING TUBES, THEN TO MOVE BACK TO CLEAR THE SEALS AND THE LATCH THE ROUNDS BEING LOADED INTO THE LOADING CHAMBERS. THE REVOLVER IS THEN FREE TO ROTATE 90* TO REPEAT THE CYCLE. THE MOTIONS ARE ACCOMPLISHED USING LINEAR HYDRAULIC ACTUATORS WITH VARIABLE ORIFICE END SNUBBERS TO CONTROL THE ACCELERATION AND DECELERATION AT EACH END OF THE STROKES TO PREVENT EXCEEDING THE STRUCTURAL LIMITATIONS OF THE ROCKETS, TO MAINTAIN CONTROL OF ROCKET POSITION AND TO LIMIT EXCITING VIBRATIONS WHICH WOULD DEGRADE THE ACCURACY OF THE LAUNCH. THE ROTATION CYLINDER CONTROLS THE ANGULAR POSITION OF THE REVOLVER BY MEANS OF A MODIFIED 90* HALF SINE WAVE CAM TRACK (PEAK OF THE SINE WAVE) MOUNTED ON THE REVOLVER ASSEMBLY. THE LINEAR STROKE OF THE HYDRAULIC CYLINDER IS THUS CONVERTED TO A 90* OF ROTATING MOTION OF THE REVOLVER. THE SAME 90* ARC BEING USED CLOCKWISE THEN COUNTER-CLOCKWISE FOR EACH SUCCEEDING CYCLE OF THE LAUNCHER&#39;&#39;S OPERATION. A RAM-RETRACT CYLINDER LOCTED ON THE CENTER LINE OF THE REVOLVER CONTROLS THE LOADING OF THE NEW ROUNDS, MOVING THE REVOLVER FORWARD TO SEAL WITH THE LAUNCH TUBES AT THE BEGINNING OF THE RAM STOKE AND RELEASING THE REVOLVER TO SPRING BACK FROM THE SEALS AT THE END OF THE STROKE, AND DEPRESSING A PLURALITY OF FIRING SWITCHES IN SEQUENCE TO OBTAIN THE MAXIMUM FIRING INTERVAL POSSIBLE WHILE THE CHAMBERS ARE SEALED TO THE LAUNCHING TUBES. THE RETURN OR RETRACT STROKE IS RAPIDLY ACCOMPLISHED TO PROVIDE TIME FOR THE LOADER ASSEMBLY LOCATED ON ITS EXTREME REAR TO PROPERLY ENGAGE THE NEW ROUNDS FOR THE NEXT CYCLE AND TO PREVENT JAMMING OF THE MECHANISM. THE ROCKETS FIRED FROM THE LAUNCHER MAY BE THE TYPE WHICH INCLUDES A PROPULSION SYSTEM HAVING A BOOST PHASE AND AN AFTER-BOOST SUSTAIN PHASE. THE ROCKET BOOST PHASE OCCURS WHOLLY WITHIN THE LAUNCHER TUBE AT ALL TEMPERATURES. THE IGNITION SYSTEM OF THE BOOST AND SUSTAIN PHASES IS INCORPORATED IN THE SYSTEM IN A MANNER WHICH INSURES THAT NO DEBRIS (WIRES, METAL PARTS, ETC.) IS EJECTED FROM THE REAR OF THE LAUNCHER TUBE ON FIRING. BOOSTER THRUST TERMINATION AND IGNITION OF THE SUSTAINER MOTOR OCCURS WITHIN THE LAUNCHER TUBE AND THE TUBE SERVES AS THE COMBUSTION CHAMBER FOR THE MOTORS.

Nov. 9, 1971 c. M. CORNELISON 3,618,453

OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed NOV. 5, 1969 llSheets-Sheet 1 Corbet M. Cornelison,

INVj'NTUR. M.

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OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed Nov. 3, 1969 llSheets-Sheet 8 m g a N o I o o o /N FIG. 2

n I H I i l g I f I I Corbe'r M. Cornelison,

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m Mg I Wu/ OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed NOV. 5,1959 C. M. CORNELISON Nov. 9, 1971 ll Sheets-Sheet 5 FIG. 4

Corbet M.Cornelison, INV NTOR.

Z w; BY I A-LZZJ 514/ #Mfk fli/fa OPEN BREECH HIGH RATE AUTOMATIC ROCKETLAUNCHER Filed Nov. 5, 1969 Nov. 9, 1971 c. M. CORNELISON llSheets-Sheet 4.

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1971 c. M. CORNELISON 3,618,453 OPEN BREECH HIGH RATE AUTOMATIC ROCKETLAUNCHER ll Sheets-Sheet 6 Filed Nov. 5, 1969 IN IENTOR "Z i j M W J #W/w A M/W Nov. 9, 1971 c. M. CORNELISON 3,618,453

OPEN BREE-CH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed Nov. 5, 1969 r 11Sheets-Sheet 7 FIG. l2

I ROCKET FIRING FIRING M PULSING SOURCE DETENT A BAND CONTACT SWITCHSWITCH FIRING FIRING ROCKET SWITCH CONTACT BAND DETENT FIG. l4

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2 M MILL/6w Nov. 9, 1971 3,618,453

OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed Nov. 3. 1969 C. M.CORNELISON l1 SheetsSheet 9 Nov. 9, 1971 c. M. CORNELISON 3,618,453

OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed NOV. 3, 1969 llSheets-Sheet 1O Corbet M. Cornelison,

1 VENTOR. M W 3 BY 04? 111% was) 1 c. M. CORNELISON 3,618,453

OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed Nov. :5, 1969 11Sheets-Sheet 11 FIG. l8

Corbet M. Cornelison, V '"NTOR.

BY MM 2w f #MMJQJ. Mm.

United Smtes Patent Ofice US. Cl. 89-1.804 7 Claims ABSTRACT OF THEDISCLOSURE An open breech, high rate, automatic, rocket launcherprovided with a pair of launching tubes and a four chamber revolving andreciprocating revolver. The revolution of the revolver allows twochambers to be aligned with the launching tubes while the other twochambers are being loaded. The reciprocating. motion of the revolverallows it to move forward to seal and align the firing chambers with thelaunching tubes, then to move back to clear the seals and latch therounds being loaded into the loading chambers. The revolver is thenfree'to rotate 90 to repeat the cycle.

The motions are accomplished using linear hydraulic actuators withvariable orifice end snubbers to control the acceleration anddeceleration at each end of the strokes to prevent exceeding thestructural limitations of the rockets, to maintain control of rocketposition and to limit exciting vibrations which would degrade theaccuracy of the launch. The rotation cylinder controls the angularposition of the revolver by means of a modified 90 half sine wave camtrack (peak of the sine wave) mounted on the revolver assembly. Thelinear stroke of the hydraulic cylinder is thus converted to a 90 ofrotating motion of the revolver. The same 90 are being used clockwisethen counter-clockwise for each succeeding cycle of the launchersoperation.

A ram-retract cylinder located on the center line of the revolvercontrols the loading of the new rounds, moving the revolver forward toseal with the launch tubes at the beginning of the ram stroke andreleasing the revolver to spring back from the seals at the end of thestroke, and depressing a plurality of firing switches in sequence to obtain the maximum firing interval possible while the chambers are sealedto the launching tubes.

The return or retract stroke is rapidly accomplished to provide time forthe loader assembly located on its extreme rear to properly engage thenew rounds for the next cycle and to prevent jamming of the mechanism.

The rockets fired from the launcher may be the type which includes apropulsion system having a boost phase and an after-boost sustain phase.The rocket boost phase occurs wholly within the launcher tube at alltemperatures. The ignition system of the boost and sustain phases isincorporated in the system in a manner which insures that no debris(wires, metal parts, etc.) is ejected from the rear of the launcher tubeon firing. Booster thrust termination and ignition of the sustainermotor occurs within the launcher tube and the tube senves as thecombustion chamber for the motors.

SUMMARY OF THE INVENTION This invention relates to a rocket launchingsystem and particularly to an open breech, high rate, automatic rocketlauncher wherein a plurality of rockets are rapidly fed into a pair oflaunch tubes while, simultaneously, a second pair of rockets are beingfired.

It is, therefore, an object of the present invention to provide an openbreech high rate automatic rocket launcher.

3,618,453 Patented Nov. 9, 1971 It is a further object of the presentinvention to provide a launcher in which a plurality of rockets areloaded in launching position simultaneously with the firing of anotherplurality of rockets.

It is another object of the present invention to provide such a launcherin which dud rounds are automatically ejected without interruption ofthe firing cycle.

It is a further object of the present invention to provide such alauncher having minimum dimensions and weight so as to permit thelauncher to be mounted on and fired from helicopters or other lightweight mounts while permitting the helicopter to maintain its stabilitycharacteristics.

It is yet a further object of the present invention to provide such arocket launcher which will minimize the effects of vibration, blast,noise, and noxious gas on personnel in the aircraft.

Other objects and advantages will be apparent after a study of thefollowing detailed description taken in conjunction with the dravw'ngswherein:

FIG. 1 is a perspective view, partially cut-away, of the launcher having missiles loaded therein.

FIG. 2 is an elevational side view of the launcher of the presentinvention.

FIG. 3 is an elevational view, partially in section, of the rear of thelauncher.

FIG. 4 is a view along line 44 of FIG. 3 and illustrates the springassembly of the loading chutes.

FIG. 5 is a sectional view along line 55 of FIG. 3.

FIG. 6 is a sectional view taken along line 66 of FIG. 3.

FIG. 7 is an elevational view, partially in section, of the revolversection and loader assembly.

FIG. 8 is a view along line 88 of FIG. 7.

FIG. 9 is a fragmentary elevational view, partially in section, showingthe revolver in aft position with one revolver chamber having a rockettherein in firing orientation, the detents for retaining the rocket inthe chamber, and a second revolver chamber in loading position.

FIG. 10 is an elevational view of the loader members and supporttherefor.

FIG. 11 is an elevational view of the loader and detent member therefor.

FIG. 12 is a plan view, partially in section of the cam dog assemblysecured to the revolver support shaft.

FIG. 13 is a diagrammatic view of the launcher of the present inventionillustrating the electro-hydraulic scheme.

FIG. 14 is a diagrammatic view of the firing circuit of the launcher.

FIG. 15 is an elevational sectional view of the ram cylinder assembly.

FIG. 16 is an elevational sectional view of the revolver rotationcylinder assembly.

FIG. 17 is a partially cut-away pictorial view of the type of missile asutilized by the launcher of the present invention.

FIG. 18 is a view of the present launcher carried by a helicopter.

DESCRIPTION OF THE PREFERRED EMBODIMENT As shown in FIG. 1, a rocketlauncher 10 includes a suppont frame 11, a loader mechanism 12, arotatable reciprocal revolver section 14, a pair of launch tubes 16 (oneremoved for clarity) and a hydraulic actuating assembly 17 forreciprocating movement of revolver 14.

Revolver assembly The revolver section includes four chambers 18 (only 2shown in FIG. 1) supported by a pair of yokes 19 and 21 concentricallyabout hydraulic actuating assembly 17. Two of the chambers are disposedfor vertical alignment with the launch tubes to fire rockets therefromwhile the other two chambers are horizontally disposed while beingloaded with another pair of rockets.

The two to one ratio of revolver cylinders to launch tubes permitsbalanced heat loads in both the revolver chambers and tubes. That is,since the rockets accelerate in the revolver chambers more heat isgenerated in the revolver chambers than in the launch tubes, thus thetwo to one ratio permits the heat to be dissipated in the pair ofchambers not being fired.

Rocket storage and loading chutes The loader mechanism (FIGS. 1 and 3)is provided with a pair of loading chutes 22 and a pair of trays 24communicating with the respective chutes. Each chute and tray isseparated by a starwheel mechanism 26. The movement of the round isdownward while in a horizontal position within the loading chute.Movement is effected by the combined force of gravity plus a leaf springassembly 28 (FIG. 4) carried in a cap 30 disposed at the top of thechutes. A plunger 31 is disposed at the base of the spring assembly forengagement with the upper rocket in the chutes. The leaf spring designprovides that the spring rate and loaded height apply a 3g load on therounds in the chutes. As the rounds are moved out of the trays to therevolver, the spring load decreases so as to always maintain a 3g loadon the rounds in the chute. The motion is intermittent, all roundsmoving simultaneously after the bottom round is rammed forward into therevolver loading chamber. The bottom round is separated from the stackabove by starwheels 26 which support the stack in a horizontal fashionto prevent jamming during the loading stage. The starwheel includes fourspokes 27 and is made of nylon and engages the rocket along the wholecylindrical body longitudinally. As the starwheel turns, the next spokeof the starwheel positions between the round in the tray and the bottomround in the chute. This allows a low friction surface on which theround to be loaded can slide without being in contact with the nextround to come down. A form sprag clutch 29 permits only one direction ofrotation of the starwheel, holds the round in the loader tray and alignsit with the revolver cylinder into which it is loaded. The two roundsare handled jointly during each ram stroke. A detent 25 is provided inthe bottom of each loading tray to engage an obturating ring of therocket to prevent forward motion of the round until the rocket is rammedforward as is discussed hereinbelow.

Loading mechanism To move the rounds into the four barrel revolversection for subsequent movement into the launch tubes there is provideda loading mechanism 32 (FIGS. 1, 3, 6, 7 and 13) powered by a hydraulicpiston 34 for forward and rearward movement of mechanism 32. Mechanism32 includes a loader arm 33 connected to piston 34 for movementtherewith and having a loader support member 38 secured at one endthereof. The piston and arm are mounted along the axis about which eachrevolver chamber 18 is concentrically disposed.

Loader support member 38 includes a pair of downwardly extendingelements 37 (FIGS. 3, 7, 8, 10 and 11) each having a loading member 40(FIGS. 1, 7, 8, l0 and 11) at the ends thereof. A spring loaded detent42 is provided at the forward end 44 of member 40 to rest in a detentring 45 of the rocket (FIGS. 1 and 17) when member 40 engages the rocketfor loading thereof, to maintain positive control over the round duringthe loading operation. Movement of piston 34 carries the loader assemblyforward and positions the rounds in the revolver chamber.

After the loader arm reaches the end of its stroke, the revolver chamberis unlatched in a manner described hereinbelow, and caused to move tothe rear to permit an angular surface 46 (FIG. 8) on the revolverchamber to engage detent 42 causing it to slide down and disengage fromrocket detent 45. The face 48 (FIG. 7) of loading member 40 remains inposition and holds the missile forward until the revolver reaches itsrearmost position and locks into the round by a separate set of detents92 (FIGS. 1 and 9) mounted in the revolver cylinders, for retention ofthe round in the revolver cylinder. A revolver rotating hydraulic pistonassembly 39 then rotates revolver 14 90 to align the two empty chamberswith the loading trays and the loaded chambers with the launch tubes ina manner to be discussed below.

To permit the loader assembly 32 to return to pick up another round forloading thereof, piston 34 is moved rearward carrying the loadingmechanism with it. As shown in FIGS.,7 and 11 loading members 40 arepivotally mounted to support member 38 at 50 and spring loaded by spring52 in the support member to retain their initial positions for theloading action. As the loader retracts responsive to rearward movementof piston 34, members 40 are forced to pivot down and ride the body ofthe next rocket to be loaded, located in the loading trays. When theloader reaches its rearmost position, loading member 40 is biased upwardby spring 52, back up behind the round and detents 42 of members 40engage rocket detent ring 45 for forward movement of the next pair ofrockets.

Obturating mechanism With a pair of rockets in the chambers aligned withthe launcher tubes, piston 34 and arm 33 move forward to carry with themthe next pair of rockets to the other two chambers of the revolver. Withthe second pair of rockets in the revolver chambers, piston 34 and arm33 move slightly forward and carries with it a pair of cam dogs 54(FIGS. 1, 6, and 12) which engage the revolver causing it to obturatefor sealing of the two vertical cylinders of the revolver with the twolaunch tubes.

To accomplish this, cam dogs 54 (FIGS. 1, 6, and 12) are secured in acam dog housing 58 which is secured to a revolver support shaft 57carried about arm 34. A revolver chamber support tube 63 (FIG. 6) isslidably mounted about support shaft 57 and is secured to yokes 19 and21 which slidably support the revolver section. Cam dogs 54 engage aplate 60 secured at the end of tube 63 to force the revolver forwardagainst the force of a spring 62 carried about the cylinder of piston 34and seated between the revolver support shaft and frame 11. The forwardmovement of the revolver forces the revolver chambers in sealed relationwith the launch tubes.

To permit engagement of cam dogs 54 with the revolver section, loaderarm 33 is provided on opposite sides thereof with a longitudinal cam 66(FIGS. 1 and 6) having a pair of forward recesses 68 and rearwardrecesses 70 at opposite ends thereof. When piston 34 and arm 33 moveforward the cam dogs rise out of forward recess 68 to ride alonglongitudinal earns 66 for engagement with pressure plate 60 of therevolver section, moving the revolver section forward into obturationposition with the launch tubes and at the same time a switch 71 isclosed firing the top tube (FIGS. 1 and 13). The ram piston 34 continuesto a second position (while revolver and tubes are obturated) until asecond switch 72 is tripped closed and the rocket in the bottom tube isfired. When the piston has reached its forward position of the stroke,the cam dogs fall into the rear recesses 70 of the cam and allows therevolver to be pushed back under force of spring 62. As the ram strokeretracts, a spring 63 (FIG. 12) rotates cam dogs 54 in an oppositedirection and allows the cam dogs to slide back along the cam trackuntil they drop back into recesses 68. During deobturation, a pulsingswitch 48 (FIGS. 1 and 13) is depressed sending a signal to a pair ofsolenoid valves 78 and 80 (FIG. 13) whichv retracts piston 34 andinitiates the next cycle by energizing the second ram assembl 39 torotate the revolver.

Revolver rotating mechanism To rotate the revolver after a pair ofrockets have fired, the second ram assembly 39 includes a piston 84(FIGS. 7, 13, and 16) provided with a rod 86 which extends out of pistoncylinder 88. Rod 86 is provided with a cam follower 89 at the endthereof which rides in a sinusoidal cam track assembly 90 disposed aboutthe periphery of the revolver section. As more clearly shown in FIG. 13,after the first pair of rockets have been fired, solenoid valve 80 isactuated to permit hydraulic fluid to move piston 84 of assembly 39 torotate the revolver section to align the second pair of chambers withthe launcher tubes. The same 90 arc is used clockwise and thencounter-clockwise for each succeeding cycle of the launchers operation.

The operating cycle requires that the revolver must rotate while therocket loader is traveling from full forward to full aft and must beheld stationary while the rocket loader is traveling from full aft tofull forward (i.e., the cycle ratio of the rocket loader valve 7 8 tothe revolver valve 80 is 2:1). When the rocket loader begins forwardtravel from full aft, the revolver will forward obturate 0.25 inch andwhen the rocket loader reaches full forward position, the revolver willrear obturate 0.25 inch. The obturating motion of the revolver willoperate pulsing control switch 48 which will provide electrical pulsesto control the rocket loader. Only the pulse from revolver rear obturatecan be used to control the rotation of the revolver.

Using basically a two stage flip flop circuit the desired control can beobtained. The pulses for control are obtained from control switch 48which is closed as the revolver completes rotation, opens as therevolver forward obturates, closes as the revolver rear obturates andopens as the revolver begins rotation. Positive pulses from the switchare inverted by an electrical signal inverter (not shown) and used totrigger the rocket loader at first stage of the flip flop. The loadersolenoid valve 78 is connected in one leg of the flip flop and one pulsewill energize and the next pulse de-energizes it, etc. The solenoidvalve 78 may be connected in either leg of the flip flop, having therocket loader travel forward when the valve is energized, or in theother leg, forward when de-energized. Triggering pulse for the revolversolenoid :80, or second stage flip flop are taken from the first stagethrough an inverter stage. The electrical control system is more fullyset forth in an application filed Feb. -4, 1966, Ser. No. 525,808, byFrank H. Case, Jr., Edgar Losberg, and Corbet M. Cornelison forElectrical Control System.

The hydraulic actuating valves are two position, two stage solenoidoperated, i.e., when the solenoid is energized the hydraulic fluid flowsin one direction and when the solenoid is de-energized the fluid flowsin the opposite direction.

The rate of fire is 400 to 450 rounds per minute, firing two rounds 50milliseconds apart on each half cycle, at present sizing andacceleration limit of the rocket. This would vary with differentrockets.

The firing of the rockets is schematically shown in FIGS. 13 and 14 andis accomplished by closing the two firing switches 71 and 72, asdiscussed above. After the rocket loader begins forward travel, thefirst switch 71 is closed completing the electrical circuit to the toprocket chamber, and as the loader approaches the end of forward travelthe second switch 72 is closed, completing the electrical circuit to thebottom rocket chamber.

To insure that the electrical circuit to the rocket is not completeduntil the revolver forward obturates and to insure that only the tworockets which are aligned with the launcher tubes will be fired, detentpins 92', carried in the revolver chambers in contact with the rocketfiring circuit, are electrically connected to switches 71 and '72.respectively, through a pair of firing springs 96 and 98 mountedexternally of the revolver section. When the revolver rotates to its 90degree rest position (in alignment with the launcher tubes) and forwardobturates, the firing springs engage the detents of the chambers inalignment with the launch tubes. The detent pins are moved inwardlyunder spring force to engage a contact band 45 (FIG. 17) on the rocket.At this point in the cycle, the ground contact and firing circuitcontacts are closed, leaving only switches 71 and 72 open. The firingswitches are closed responsive to revolver movement as described, supra,and as shown in FIGS. 13 and 14, to launch the rockets in sequence Whichpermits the maximum time interval between the pair of rockets which isconsistent with the ignition delays, thrust build up and gas evaculationtimes predicated by the rocket characteristics interrelated with thelauncher.

As shown in FIG. 17, rocket 20 is generally shown to have booster andsustainer motors and 102, respectively. An obturating ring 104 islocated just aft of head 106. This ring prevents booster motor gasblow-by and can act as the ground leg of the firing circuit. The ring ismade of brass and is slotted at 107 to reduce the friction load createdby the fit of the ring in the tube. Silicone rubber is potted in thegroove to seal the slots.

A single nozzle assembly 108 serves both the booster and the sustainermotors.

Four fins 109 are secured to the aft periphery of the rocket. The finsare spring loaded by springs 110. When the rocket is in the launcher,the fins are held down by a nylon cord which burns during the boostphase and frees the fins so they can be extended outwardly by spring110.

The ignition and retention ring or detent 45 is secured to the nozzleassembly. The ignition ring includes a contact band 114 electricallyisolated from the metal parts of the missile and electrically connectedto squibs (not shown) in the booster and sustainer motors. The launcherdetent pin fits into the contact ring and holds the rocket in positionduring loading and cycling operations.

As shown in FIG. 18, launcher 10 is mounted on a helicopter. Onelauncher is mounted on each side of the aircraft. When installed, theweapon has the capability of firing from 15 degrees elevation to 20degrees depression. The limiting factor is the rotor blade. Hydraulicpower for the system is available from the hydraulic system of thehelicopter.

I claim:

1. An open breech, high rate, automatic rocket launcher comprising:

(a) storage means having a plurality of rockets therein, said storagemeans including a pair of trays each having a single rocket therein;

(b) support means having a pair of launch tubes secured thereto;

(0) a revolver section having a plurality of chambers therein; saidrevolver section disposed for rotary movement for alignment of a firstpair of said plurality of chambers with said launch tubes and forreciprocating movement between said storage means and said launch tubes;

(d) firing circuit means disposed for ignition of the motors of saidrockets in said first pair of chambers;

(e) loader means including a pair of arms respectively slidably carriedin said trays for engagement with said rockets therein for moving saidrockets from said trays to a second pair of said plurality of chambersof said revolver section, said means including motion transmitting meansdisposed for moving said arms from a first position of enagement withsaid rockets in said trays to a second position of disengagement fromsaid rockets in said second pair of chambers, said loader means disposedfor displacement to a third position for energization of said firingcircuit for ignition of the motors of said rockets in said first pair ofrevolver chambers which are in alignment with said launch tubes whilesimultaneously loading rockets in said second pair of chambers which arenot in alignment with said launch tubes.

2. A rocket launcher as set forth in claim 1 wherein said storage meansincludes a pair of loading chutes having said plurality of rocketstherein and said pair of trays being disposed beneath said chutes toreceive rockets therefrom, said loader means disposed for engaging saidrockets in said trays for movement thereof to said revolver chambers.

3. A rocket launcher as set forth in claim 2 including means forconnecting said motion transmitting means to said revolver section forreciprocating movement thereof from a first position of engagement withsaid storage means to a second position of engagement with said launchtubes for sealing engagement between said first chambers and said launchtubes.

4. A rocket launcher as set forth in claim 3 including second motiontransmitting means disposed for rotating said revolver section foralignment of said second pair of chambers responsive to firing saidrockets from said second pair of chambers.

5. Apparatus as in claim 4 wherein said first transmission meansincludes a hydraulic cylinder having a piston slidably secured thereinand connected to said loader arms for movement thereof.

6. A rocket launcher as set forth in claim 5 wherein 8 said secondmotion transmission means includes a second hydraulic cylinder having apiston slidably secured therein; and

means connected to said piston for transferring linear movement of saidpiston to rotary movement of said revolver section responsive to firingsaid rockets from said first pair of cylinders.

7. A rocket launcher as set forth in claim 6 including air transportmeans for transporting said launcher to a target.

References Cited UNITED STATES PATENTS 1,709,399 4/1929 Herlach et a1.89-33 B 2,453,830 11/1948 Chadwick et al 8933 B 2,594,199 4/1952 Motley89-33 B 2,972,286 2/1961 Marquardt 89-155 X 3,331,284 7/1967 Case, Jr.et a1 89l35 X SAMUEL W. ENGLE, Primary Examiner U.S. Cl. X.R.

